Safety landing device



Patented Apr. 30, 1946 UNITED STATES PATENT'DFFICE vSAFETYLANDING'ISEVICE' y Raymond L. Freas, Conshohocken, Pa. v ApplicationSeptember 25, 1942, 'Serial No.14579,v64l

14 claims. (o1. 244%138) l (Granted under the act of Marchl3,1883,.amended April 30, 370 k0.,(r. 57.)

This invention relates to safety landing devices and more particularlyto a safety landing device for a radio transmitting or receivingapparatus, or other apparatus which is subject to injury by themechanical shocks resulting from hard landings when the apparatus isdropped from van aircraft to the ground. f l i In supplying airbornetroops with communication equipment or other supplies, it is necessarytodrop these supplies from an aircraft. yIn those instances wherein theequipment to be used `by `the troops is subject to injury by mechanical:it houses or supports.

It is also realized that means mustf'be provided to absorb the shockresulting fromthesu'dden Vdeceleration of the apparatus upon the openingvof the` parachute and that the ysecuring means for said parachute mustbe releasable upon ,convtact with the earths surface to prevent theAparachute from dragging the apparatus over rough terrain and therebysubjecting it to further possible injury. It istherefore an object ofthis-invention to provide a compact shockproof support or chassis for aradio apparatus which permits successful dropping of the radio apparatusfrom aircraft to the ground, as for the `use' by Yparachute troops orother troops or persons marooned without communication. o

It is also an object of this invention to provide means for securing theparachute to the apparatus 'adaptedto be dropped from the aircraft whichoperates upon contact of the apparatus Vwith the earths surface torelease the said apparatus frcmrengagernent with the parachute.

It is also a further object of this invention to provide shock absorbingmeans operable lupon the opening of said vparachute to prevent thesudden shock thus developed from being transmitted directly to theapparatus carried thereby. Attention is invited topa copendingapplication Serial No. 452,616, filed July 28, 1942, for a Radio driftbomb. This copending application discloses the features of thisinvention in an apparatus utilized for obtaining the drift angle of anaircraft by means of radio bearings.

In the single and preferred embodiment of the invention disclosed inthis applicatiomparticular reference is had to the drawing, inY whichFig`.f1 is ar longitudinal cross-sectionalview of a radio container andparachute adapted to be dropped from an aircraft; 'l 'y Fig. 2 is anenlarged cross-sectional view of the friction and inertia meansI forabsorbingl the shock developed by the vopening of the parachute; Fig. 3is a perspective lview of a reel containing the cable for Supporting theradio` container; d 4 is a detailed'perspectiveview of the parachutereleasing mechanism; d Figi Slisa plan viewftaken on line S-'of Fig.'l'fandf l. ,4 y v .f fjFig. 6 y'isya'fragmentary enlarged view oftheparachute housing-showing a bayonet slot for releasably securing the`parachute compartment to the compartment containing the radio'.transmitting apparatus'.

'Referring 'now Ato i the drawing and particular- *ly-'tofFigg 1 whichillustrates the general combination `of 'acompartment formed iby the"cylindrical casing In adapted tocontain a' radio transjmitti'ngapparatus and/power supply source therefor and' a parachute'.compartment formed by asecond cylindrical casing: II. One "endof thecasing l0 is secured :to an intermediate disklikek bulkhead I3 by havingits cylinderedge insertedl into' a complementary peripheral groove I9lformed in the under surface of the bulkhead i3."V The ,screws'l arethreaded through aligned openingsformed in the bulkhead I3 and thecasing'lll'lto retain the edge -of the Vcasing tightly against` asuitable gasket v disposed in the bottom ofthegroove.' I8 so as to forma water-tight en- :closurel at the'ju'nctionlof the bulkhead I3 and thecasing IUJQA plurality of bayonet slots 8' are provided in the edgesurfaceof the second casing Il'so that thisy casing` may be removablysecured to Lthe bulkhead. [3 by. having these slots 8 engage the screws8 whichextend across a groove 'Il when'the 'cylindrical edge of thecasing l! is insertedinto the said circumferential groove Il.

A disk lllwand cap AI 5 are secured together and are secured -als otothe .open end ofthe casing I0 to: complete, a water-tight enclosurewhich houses the radio transmitting apparatus. Since the details oftheradio transmittingapparatus form no partof thefpresent invention, vtheyare not disclosed... However, in the preferred embodiment of myinvention,zthe radio transmitting apparatus is suitably secured to theconcentric disks 83'1and'84 of the lchassis which isV indicated on thedrawing at I6. The enclosure formed by the casing Il) houses in'addition to the radio transmitting apparatus and the support for thechassis I6 a suitable power pack (not shown) which supplies thenecessary electrical energy for the radio transmitting apparatus. Whilethe details of the power pack are not disclosed, I prefer to secure thepower pack to the concentric disks 84 and 85 so that the power pack willbe supported and'retained within the space defined by these twoconcentric disks.

The support for thechassis is positioned centrally within the casing land comprises speciiically a hollow metallic tube 34 into one end'l ofwhich is inserted a tap threadedcollar ..38

which is welded or otherwise secured thereto.

This end of the tube 34 is then threaded onto the projecting end of thehollow friction bushing 48 positioned centrally within the cavity 36cable is coiled and contained between the upper and lower disks and 16in the space provided by the center recess 18 cut out of the undersurface of the top disk 15. One end of the cable is led out through theopening 19 formed in the disk 15 to extend upwardly through the interiorof the inner tubular member 4| to engage the fhook 68 as is clearlyshown in Fig. 2. The other end of the cable extends through the'curvedslot 16' cut in the under surface of the disk 16 and lis anchored to thebar 13. Upon withdrawal of the cable '1| from the space 18 formed by theVinner disk 16 and the upper disk 15, the entire reel which consists oithese two disks and the formed in the disk i4. The tube 34, collar 38and bushing 48 are retained in place Ibymeans of a through pin 9. Theother endof .thetube 34 projects outwardly through anopening 3'9 ofrthebu1k1iead I3 and issealed tothis bulkhead by meansof the collar 31'so -as toform afwatertight connection therewith. The Vtubell performsthe dual function of providing asupport for the .chassis I6andcooperating with the inner .tubular member 4| to provide ayieldablemeans frictionally absorbing'the force set up by the sudden.deceleration ofthe radio transmitting apparatus upon Vthe initialopeningof the parachute. The inner tubular member 4| has a collar 45secured toits lower end in.frictionalengagement 'with the tubularsupport;Y 34. When a force sui- .62 is clamped in, a .fixedr position toa channel member 65 by means `of vspring clips B3 and 64.`

V'Ifhis channel member .65 is securely fastened to the straightshankportion 69 of the V-shaped 'nook V68 .by means ofi the through pins61. The .V-shaped hook 68 issecured .tothe` inner tubular the shroudring `t2V to jbe pulledfre'elof its fixed positioncn the channel member65 .by the parachute shrouds Bl and into engagement with the hook B9when the parachute is linitially opened.

A cable 1| connects .the hook' with the bottom vby the cable andtransmittedtoY thejbottom of the radio casing assembly. The cable orwire 1| also serves the function of positioning the support below thecenter-of'gravity ofthe radio casing assembly; Y

A rotatable reel 12 is provided for the cable 1| to contain the coiledcable and permit the cable to be played out without acquiring twistsor'kinks as the inner tubular member 4| is extended. vThis reel is`clearly shown in Figs. 2 and 3 and consists specically of an anchoringbar 13 `to which the cable 1| is securely fastened. The anchoring bar 13has a projection 14 which forms a friction bearingsurfacewith .the capmember l5. The

' VThe disks are maintained in anchoring bar 13 will be free to rotateabout a vertical axis in the space provided by the cap lfand the bottomdisk lll. The ange bushing 40 facilitates rotation of the reel 43 toautomatically prevent the twists or kinks from being formed inthe cableor wire 1|.

` Referring again to Fig. 1 wherein the details of the Support for theradio transmitting apparatus and the power packV are disclosed, the disk8B .is rigidly attached by means of the collars 8| .and 82 to theexterior tubular supporting member Y34. The position of the .disk 88 maybe adjusted axially along the supporting .member34 by means of the setscrews. The. chassis I6 of the radio transmittingapparatus and powerpack consists.. speciiically ofV 4three concentric disks or` plates'83,Stand 85,'each of which; is supported so-as to be free tofmovevertically along vthe tubular supportingmember '34. Rubber eyelets 9 i,92 and S3 are provided between the .tubular support 34. and the.concentric ldisks .at

V83.84 and 35, respectively, for the purpose of .absorbing shocks andvibration.

` the illustrated position axially spaced along the tubularsupportmember lu'` V'rhesprmg clips es and-Mpermit 50 l.ing member 34'by .means of `i-,hreeedually spaced .supporting.rodsv 86. Rigidlyattached tothe disk 8|! Aarela:plurality .of axiallyV extendingjrods 81.

of therubber grommets 88 whichf are Ysetillto the disk 83. These'grommets permitllmoveinentlof Athe. chassis I8 axially along the tubesupporting member 34' and relative to the disk 8 0 andjprevent themechanical shock of landing from being V,transmitted directly to theradio transmitting apparatus which i's to be. supported onthese disks.

'The disk 8 5 Ais also secured to the diskjll and spaced axiallytherefrom by. means of the spacing rods 186so as to provide 'a space forthepower pack which comprises the source oi .electrical energy for theradio transmitting apparatus.V It should thus be apparent that aplurality 'of disks "are resiliently and slidably supported in-parallelalignment in an adjustable position along the tubular -support3ll andthat resilient means is also provided for attaching the disks totheadjustable securing means at points which are substantiallyequi-angularly spaced about the center vtubular supporting member.

The operation of the apparatus'is as"fc' llo'\'vs:`

When dropping the Vapparatus from an aircraft, the casing Il is severedfrom engagement with the casing l0 by turning the handle l2 t0'disengage' the vbayonetslot 8" from thescrew 8 and to provide a releasefor the parachute 85. -When the parachute 60 opens, the shroud ring' GZis pulled free of the spring clips'63 and 84 andint'o engagement withthe hook 68, The forces set up by theopening of the parachute and theretardation of the casing I8 will be transmittedthrough the hook B8 tothe inner tubular member 4'! causing'this -inner tubular member to.bef-extended 4I. is-extended to at least partially absorb the shockproduced by the opening .of the parachute.

Before the parachute is opened and before the inner tubular member 4|has been extended, the cable Il is coiled within the void space 18 ofthe lreel assembly 12 and has an end secured to the anchoring bar '13thereof. As the 'inner tubularA member4l is being extended, however,thecable 1| which is fastened tothe upper 'end lof this tubular memberis'removed from its reel 12 by being played out and run up on the-insideof this tubular member. The reel 'l2 rotates freely about the verticalaxes thus preventing the formation of twists or kinks Within the cableor Wire 'H -as -the cable is completely uncoiledy to take up theforceftransmitted by the parachute'fand transmit'this force to theanchoring bar-13 positioned at the lower end ofcasing l0.' 'v l i Afterthe casing VIl) haslighted upon a'land surface, the pull of theparachute-'5'upon the shroud 'ring 62 is released and the ring is freeto fall by gravity and its inertia over the open end of the hook B8 thusdetaching the parachute vfrom ,the4 casingk l0.V The channelkl member*65 which is secured to the inner endof thetubular member 4| restrainstheshroud?ijingglizvsQthat it can'fall only inone direction,that'directi eing over the open end ofthe hook. In this manner, theparachutewill b'ereleased from'v its engagement with the casing l0immediately after the the United States of America for governmentalpurposes without the payment of any royalties thereon or therefor.

I claim:

1. A safety landing device for apparatus adapted to be dropped from anaircraft comprising the combination of a tubular casing, closures ateach end thereof, a rigid tubular support secured substantially at eachend t0 said closures and extending axially of said casing, a membercontained within said tubular support, a hook having a straight shankportion secured to said member, a parachute having shrouds and a shroudring secured thereto, a channel member, means securing said channelmember to said hook with the shank portion thereof lying within saidchannel, and spring slips secured to said channel mem-ber for engagingsaid ring to releasably retain the said ring in the xed position on4said channel for engagement with said hook when said ring is pulledfree of said clips by the opening of said parachute whereby said ringwill be free to wchute., l ,2.:A safety landing 4device for an apparatusto' fall by gravity over-the open end of to-release said parachute; v

. 5. `A safety landing apparatus adapted to withstand the shock oflanding by parachute compris- 'slide-'over the vopen endiof said hookafter the apparatus has been safely landed by said paraadapted to. bedropped from an aircraft comprising the combination of a tubular casingadapted to house the said apparatus, separate means closing each end ofsaid casing, a fixed tubular mem- -ber extending substantially axiallyof said casing J secured at itsv end portions to each of said means,

and passing through a first one of saidseparate means,.a secondtubularmember contained within the xed tubular member to frictionally engagethe innerV surface thereof, a parachute, and means extending through theend of said fixed tubular member passing through the first one of saidseparate'means for securing saidV second member to said parachutewhereby said second tubular inember. will be extended from the end ofsaidv iixed 4tubular vmember when the force produced by the decelerationof said apparatus upon the opening 1ofsaid-*parachute'exceeds the totalfrictional resistance between .said tubular members.

The device dened in claim 2 characterized further by the additionthereto of a cable securing an end of said second tubular member to thesecond one of said separate means and rotatable meansv for paying outsaid lcable to: prevent the .formation of twists therein as the `secondmem- Asaid ring in a iixed position relative to said hook to engage thelatter as the parachute opens, and

lmeans blocking motion of vsaid ring in any directionotherthanovertheopen end of said hook whereby as said casing lands saidV ring will befree the hook ing a tubular casing, means for closing each end of saidcasing, a tubular support extending substantially axially of said casingsecured at its end portions to each of said means and passing throughone end of said means, means forming a shockproof support for saidapparatus adapted to be housed in said casing comprising a plate havinga central opening for said tubular support, means suitably securing saidplate along the length of said tubular support, a second plate having acentral opening for said tubular support, and means resilientlyattaching said second plate to said rst plate and to said tubular`support.

6. The device described in claim 5 wherein said tubular casing andtubular support are cylindrical and said rst and second plates arecircular.

'7. In a safety landing device for apparatus adapted to be dropped froman aircraft, a shockproof chassis for said apparatus comprising atubular casing, closures for each end of said casing,

a rigid support secured substantially at each end of said closures andextending axially of said casing, a rst plate having a center opening,means adiustably securing said i'lrst plate along the length of saidsupport, a resilient eyelet mounted on and adjustable along the support,a second plate secured at its center portion to said eyelet, and meansresiliently attaching said second plate to said rst plate in spacedparallel relationship.

8. The device described in claim 7 wherein a second resilient eyelet isadjustably positioned on said support and a third plate is secured tosaid second eyelet `and resiliently 'attached to said-ist plate." 1 .l Y1.2.

9. A device providinga shockproof support-for apparatus comprisingY ayplurality of disks having central openings, fandi'a'centralsupportresiliently andrslidably supportingysaid' disks .in parallelalignment; rst `means adjustably xed to 1a portion of said supportandsecond .means resiliently `A'attaching said disks to said rst meansat points spaced substantially equi-'angularly about ysaid centralsupport.

10. VA safety landing device for apparatus adapted to be droppedzfrom-an aircraft comprising in combination a casing adapted to housesaid apparatus, a tubular member, means `securing ksaid -tubularmemberto :said casing, a sldahle :member Vwithin saidl tubular member, saidmember being Africtionally engaged with the innersurface 'of saidtubular member, `aparachute including 'shrouds and a shroud ring, andmeans 1 connecting said shroud ring to said slidable memberfwhereby thelatter will move Withinsaid tubular member when the force produced 'bythe deceleration of said apparatus andcasingupon the opening of said'parachute exceedsV the total frictional resistance between said tubularmember and the member slid-Y `able therein. Y A 1 l1. A safety landingdevice for apparatus `adaptedfto beidroppe'd from analrcraft comprisingin combination a casing for housing 'said apparatus, jatubularfqmemberwithin jsai'd casing,

' said memberextending axially of said casing and protruding'through anlend Wall thereof, 'akslidable member contained withinsaid'tubula-member, a parachute .having shrouds and a'shroud.

rotsaidiclip' means fby. the opening of'said'ipara- "chutefand wherebysaid ring will be Vfreetolslitie overlthe fopen end of said hookaftersaid casing has beenrlanded by said parachute'.v 1

1-2. lAsafety landingI apparatus adapted towithstand. the shock oflanding byp'arachute comprising Vin combination a casing, a support rod,'said `rodffoeing vsecured within said casing. and extending Aaxiallythereof, means forming a, shockproof support for apparatus adapted to behoused `Within said casing including a rst plate having a`centralopening for said support rodjmeans -securing said firstplate tosaid support rod, a secsupport, a second plate having a central openingtherein andgsecured at its central portion to said eyelet., and v`meansresiliently.connecting vsaid second plate tohsaid rst plate, saidapparatus being `adapted to be carried upon said secondplatefjA l4i In asafety landingl device for apparatus adapted to be-dropped from anaircraft, the combination comprising, a casing adapted to house:said'apparatus a support rod securedwithin and extend-ing axially of:said casing, a Vplatefmember having a central opening therein throughwhich saidsupport rod passes, -rst means xed to a portion-of saidsupport, .and second :means resiliently Qeonnectingsaidplate membertosaid rst means,

platernember..

`Asaid fapparatus 4being adapted tobe carried by said

